def __init__(self, kind, speed, altitude, payload_released=0,
atmosphere=None,
release=None, *args, **kwargs):
self.kind = kind
if 'weight_fraction' not in kwargs and kind in self._WEIGHT_FRACTIONS:
self._weight_fraction = self._WEIGHT_FRACTIONS[kind]
else:
self._weight_fraction = kwargs.pop('weight_fraction', None)
self.altitude = altitude
self.payload_released = payload_released
self.atmosphere = Atmosphere() if atmosphere is None else atmosphere
self.density = self.atmosphere.density(altitude)
self.release = release
if speed is not None:
self.speed = speed * 1.68780986 # kts to ft/s
self.mach = self.speed / self.atmosphere.speed_of_sound(altitude)
self.n = 1
if 'turn_rate' in kwargs:
turn_rate = kwargs.pop('turn_rate')
self.n = sqrt(1 + (turn_rate * self.speed / G_0) ** 2)
if 'turn_radius' in kwargs:
turn_radius = kwargs.pop('turn_radius')
n = sqrt(1 + (self.speed / turn_radius / G_0) ** 2)
if hasattr(self, 'n'):
self.n = max(n, self.n)
self.climb_rate = kwargs.pop('climb_rate', 0)
self.acceleration = kwargs.pop('acceleration', 0)
self.dynamic_pressure = 0.5 * self.density * self.speed * self.speed
for key, defaults in self._DEFAULTS.items():
if key in self.kind:
for var, default in defaults.items():
setattr(self, var, kwargs.pop(var, default))
if 'cruise' in self.kind or 'dash' in self.kind:
self.range = kwargs.pop('range')
self.time = self.range / speed
if len(kwargs) > 0:
warn("Unused kwargs: {}".format(kwargs.keys()))
class Segment(object):
"""
Aircraft mission
:param kind: the type of segment, e.g., takeoff, cruise, dash, loiter, land
:param speed: the speed at which the segment is to be flown (knots)
:param altitude: the altitude at which the segment will take place (ft)
:param atmosphere: the atmosphere instance that contains the sea level conditions, if None s provided, a standard one is created
:type kind: str
:type speed: float
:type altitude: float
:type atmosphere: ::class::`Atmosphere`
If mission is of type `cruise`:
:param range: the range to fly during the segment (nmi)
:type range: float
If mission is of type `loiter`:
:param loiter_time: time to loiter (hrs)
:type loiter_time: float
"""
_DEFAULTS = dict(warmup=dict(time=60.0),
takeoff=dict(field_length= 1500,
mu=0.05,
time=3,
obstacle_height=100),
land=dict(field_length=2500,
mu=0.18,
time=3,
obstacle_height=100),
loiter=dict(time=None),
)
_WEIGHT_FRACTIONS = dict(warmup=0.99,
taxi=0.99,
takeoff=0.98,
climb=0.95,
descend=0.98,
land=0.99,
)
def __init__(self, kind, speed, altitude, payload_released=0,
atmosphere=None,
release=None, *args, **kwargs):
self.kind = kind
if 'weight_fraction' not in kwargs and kind in self._WEIGHT_FRACTIONS:
self._weight_fraction = self._WEIGHT_FRACTIONS[kind]
else:
self._weight_fraction = kwargs.pop('weight_fraction', None)
self.altitude = altitude
self.payload_released = payload_released
self.atmosphere = Atmosphere() if atmosphere is None else atmosphere
self.density = self.atmosphere.density(altitude)
self.release = release
if speed is not None:
self.speed = speed * 1.68780986 # kts to ft/s
self.mach = self.speed / self.atmosphere.speed_of_sound(altitude)
self.n = 1
if 'turn_rate' in kwargs:
turn_rate = kwargs.pop('turn_rate')
self.n = sqrt(1 + (turn_rate * self.speed / G_0) ** 2)
if 'turn_radius' in kwargs:
turn_radius = kwargs.pop('turn_radius')
n = sqrt(1 + (self.speed / turn_radius / G_0) ** 2)
if hasattr(self, 'n'):
self.n = max(n, self.n)
self.climb_rate = kwargs.pop('climb_rate', 0)
self.acceleration = kwargs.pop('acceleration', 0)
self.dynamic_pressure = 0.5 * self.density * self.speed * self.speed
for key, defaults in self._DEFAULTS.items():
if key in self.kind:
for var, default in defaults.items():
setattr(self, var, kwargs.pop(var, default))
if 'cruise' in self.kind or 'dash' in self.kind:
self.range = kwargs.pop('range')
self.time = self.range / speed
if len(kwargs) > 0:
warn("Unused kwargs: {}".format(kwargs.keys()))
@property
def weight_fraction(self):
if self._weight_fraction is not None:
return self._weight_fraction
else:
tsfc = self.aircraft.engine.tsfc(
self.mach, self.altitude, self.afterburner)
t_to_w = self.aircraft.t_to_w * \
self.aircraft.thrust_lapse(
self.altitude, self.mach) / self.prior_weight_fraction
return 1 - exp(-tsfc * t_to_w * self.time)
self.aircraft.mach = self.mach
c1, c2 = self.aircraft.engine._tsfc_coefficients
u = (self.aircraft.cd + self.aircraft.cd_r) / self.cl
return exp(-(c1 / self.mach + c2) / self.atmosphere.speed_of_sound(altitude) * ())
def thrust_to_weight_required(self, aircraft, wing_loading, prior_weight_fraction=1):
if self.speed == 0:
return [0.0] * len(wing_loading) if hasattr(wing_loading, '__iter__') else 0.0
self.aircraft = aircraft
self.prior_weight_fraction = prior_weight_fraction
self.afterburner = self.aircraft.engine.afterburner and 'dash' in self.kind
aircraft.mach = self.mach
cd_0 = aircraft.cd_0
k_1 = aircraft.k_1
k_2 = aircraft.k_2
if self.release is not None:
self.aircraft.stores = [store for store in self.aircraft.stores if store not in self.release]
alpha = aircraft.thrust_lapse(self.altitude, self.mach)
beta = self.prior_weight_fraction
cd_r = aircraft.cd_r
t_to_w = None
if 'takeoff' in self.kind:
aircraft.takeoff
k_to = aircraft.k_to
cl_max = self.aircraft.cl_max
self.aircraft.cl = cl = cl_max / (k_to * k_to)
xi = self.aircraft.cd + cd_r - self.mu * self.aircraft.cl
t_to_w = linspace(0.01, MAX_T_TO_W, 200)
a = k_to * k_to * beta * beta / (self.density * G_0 * cl_max * alpha * t_to_w)
a = - (beta / (self.density * G_0 * xi)) * log(1 - xi / ((alpha * t_to_w / beta - self.mu) * cl))
b = self.time * k_to * sqrt(2 * beta / (self.density * cl_max))
c = self.field_length
w_to_s = power((-b + sqrt(b * b + 4 * a * c)) / (2 * a), 2)
self.aircraft._takeoff = {'w_to_s': w_to_s, 't_to_w': t_to_w, 'a': a, 'b': b, 'c': c}
return interp(wing_loading, w_to_s, t_to_w)
if 'land' in self.kind:
aircraft.landing
k_td = self.aircraft.k_td
cl_max = self.aircraft.cl_max
self.aircraft.cl = cl = cl_max / (k_td * k_td)
if aircraft.reverse_thrust:
alpha = -alpha
else:
alpha = 0.0
# assume drag chute
cd_chute = 0.0
if self.aircraft.drag_chute is not None:
drag_chute_diam = self.aircraft.drag_chute['diameter']
drag_chute_cd = self.aircraft.drag_chute['cd']
try:
wing_area = self.aircraft.wing.area
except AttributeError:
wing_area = 500
warn("Could not get an area for the wing (self.aircraft.wing.area), assuming 500 sqft")
cd_chute = drag_chute_cd * 0.25 * drag_chute_diam * drag_chute_diam * pi / wing_area
xi = self.aircraft.cd + cd_r - self.mu * self.aircraft.cl + cd_chute
t_to_w = linspace(0.01, MAX_T_TO_W, 200)
a = (beta / (self.density * G_0 * xi)) * log(1 + xi / ((self.mu + (alpha / beta) * t_to_w) * cl))
b = self.time * k_td * sqrt(2 * beta / (self.density * cl_max))
c = self.field_length
w_to_s = power((-b + sqrt(b * b + 4 * a * c)) / (2 * a), 2)
self.aircraft._land = {'w_to_s': w_to_s, 't_to_w': t_to_w, 'a': a, 'b': b, 'c': c}
return interp(wing_loading, w_to_s, t_to_w)
aircraft.configuration = None
q = self.dynamic_pressure
c_l = self.n * beta * wing_loading / q
excess_power = self.climb_rate / self.speed + self.acceleration / G_0
# Master Equation from Mattingly, 2002
return (beta / alpha) * (q / (beta * wing_loading) * (k_1 * c_l * c_l + k_2 * c_l + cd_0 + cd_r) + excess_power)
